EP2230394B1 - Composant utilisable dans des écoulements de gaz chaud - Google Patents

Composant utilisable dans des écoulements de gaz chaud Download PDF

Info

Publication number
EP2230394B1
EP2230394B1 EP10154480.7A EP10154480A EP2230394B1 EP 2230394 B1 EP2230394 B1 EP 2230394B1 EP 10154480 A EP10154480 A EP 10154480A EP 2230394 B1 EP2230394 B1 EP 2230394B1
Authority
EP
European Patent Office
Prior art keywords
component
ceramic material
fibre
region
flow edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP10154480.7A
Other languages
German (de)
English (en)
Other versions
EP2230394A2 (fr
EP2230394A3 (fr
Inventor
Dr. Martin Friess
Markus Keck
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP2230394A2 publication Critical patent/EP2230394A2/fr
Publication of EP2230394A3 publication Critical patent/EP2230394A3/fr
Application granted granted Critical
Publication of EP2230394B1 publication Critical patent/EP2230394B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/90—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using deflectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/665—Steering by varying intensity or direction of thrust characterised by using a nozzle provided with at least a deflector mounted within the nozzle
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y10T428/24612—Composite web or sheet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree

Definitions

  • the invention relates to a component for use in hot gas flows.
  • thrusters are also referred to as jet flaps or rudder. They are arranged near an exit end of a nozzle of a flying object and serve to influence the hot gas flow immediately before the exit in order to be able to steer the flying object.
  • Hot gas flows often contain particles, in particular when solid fuels are used.
  • a charged with a hot gas flow component such as a thruster is therefore regularly loaded both aerodynamically and by impingement of abrasive and / or corrosive particles.
  • a thruster for use in hot gas flows with a wing wherein the wing is made of a fiber reinforced ceramic material, the fiber reinforced ceramic material is made by continuous fabric layers and the material for a core portion of the wing has a higher ceramic content than a deck area on both sides of the core area.
  • a missile having a nose tip, fixed fins or movable rudders, thrusters, thrusters and nozzle neck inserts, combustor liners, tail cones, lattice vanes, fluidics and a radome is known, which components are made of ceramic material.
  • a nozzle assembly that includes thrusters that are pivotally mounted about an axis.
  • a rocket motor which comprises thrusters in an engine nozzle.
  • the invention has for its object to provide a component for use in hot gas flows, which has a high resistance to both aerodynamic and abrasive loads.
  • the component has a first region of fiber ceramic material, a second region of fiber ceramic material and a middle layer of fiber ceramic material disposed between the first region and the second region wherein the fibrous ceramic material of the middle layer has a lower ceramic content than the fibrous ceramic material of the first region and the second region, and that at least one acute angled leading edge and / or trailing edge of the component is formed on the middle layer.
  • the ceramic content influences the properties of a fiber-ceramic material that are relevant for use in hot gas flows.
  • An increase in the ceramic content is on the one hand with an increase in the abrasion and corrosion resistance, on the other hand accompanied by a reduction in the mechanical strength, in particular the compressive and tensile strength.
  • high mechanical strength is a prerequisite for high stability against aerodynamic loads.
  • the middle layer of the component according to the invention can be advantageous as an aerodynamically supporting layer due to their relatively high mechanical strength serve the component.
  • the component is protected by the choice of the material of the first and of the second region, between which the middle layer is arranged.
  • Leading edges and outflow edges are edges, via which in each case two flow guide surfaces of the component, along which a hot gas flow is guided during the use of the component, are connected to one another.
  • Two flow guide surfaces can meet directly with the inclusion of an angle, so that the edge has a finite longitudinal extent, but no finite transverse extent transverse to the longitudinal extent.
  • the angle at which the flow guide surfaces meet defines in this case the edge angle.
  • two flow guide surfaces can also be connected to one another via a separate surface section of the component.
  • the edge is formed by this surface portion and has both a finite longitudinal extent and a finite transverse extent transverse to the longitudinal extent.
  • Edge angle is here the angle given in a plane perpendicular to the longitudinal extent of the edge between the tangent planes of the flow guide surfaces at the points where they are adjacent to the edge, respectively.
  • a finite transverse extent in particular also have rounded edges.
  • the component When the component is used as intended, the component is oriented such that a leading edge points in a direction which is essentially opposite a flow direction of the hot gas flow, while an outflow edge points in a direction substantially parallel to the flow direction of the hot gas flow.
  • At least one acute-angled leading edge and / or trailing edge of the component ie at least one leading edge and / or Trailing edge with a sharp edge angle, formed on the middle layer.
  • This refinement increases the stability of the component at the at least one leading edge and / or trailing edge.
  • the probability of breakage at this at least one edge is reduced, as is frequently observed in hot gas flows and can lead to a substantial inoperability of the component.
  • Swinging on an acute-angled leading edge or trailing edge occurs less frequently if the material of the region on which this edge is formed is specifically optimized with regard to its mechanical strength, as is the case with the middle layer.
  • a high mechanical strength of the region of the edge of relatively greater importance than a high abrasion resistance is to avoid breaking as much as possible.
  • the at least one leading edge and / or trailing edge is formed at least over a part of a finite longitudinal extension at the middle layer.
  • the at least one leading edge and / or trailing edge is formed over its entire longitudinal extent at the middle position.
  • the at least one leading edge and / or trailing edge has a finite transverse extent transverse to its longitudinal extent.
  • the at least one leading edge and / or trailing edge may be rounded. Edges with a finite transverse extent exhibit increased stability against abrasive and corrosive stresses in a hot gas flow compared to edges without finite transverse extent.
  • the at least one leading edge and / or trailing edge has a finite transverse extent, it is favorable if it is formed at least over a part of its transverse extent at the middle position.
  • the at least one leading edge and / or trailing edge is formed over its entire transverse extent at the middle position.
  • both the at least one leading edge and / or trailing edge are formed over their entire transverse extent as well as at least one adjacent to the at least one leading edge and / or trailing edge edge near portion of a flow guide surface of the component to the middle layer. In this case, a particularly extensive reduction in the probability of breakage at the at least one leading edge and / or trailing edge is achieved.
  • a course of the middle layer is parallel to the longitudinal extent of the at least one leading edge and / or trailing edge. Then, the at least one leading edge and / or trailing edge, in particular over its entire longitudinal extension, can be formed on the middle layer in a targeted manner, while the flow guide surfaces for the most part at other areas of fiber ceramic material, for example be formed on the first or second region, and thus can be optimized in terms of their abrasion resistance.
  • an angle bisector of an edge angle of at least one leading edge and / or trailing edge within the component in the middle position can make a particularly high contribution to increasing the stability of the component.
  • such a structure makes it possible to form two opposing leading edges and / or trailing edges of the component both at the middle layer.
  • a simple construction of the component results when an angle bisector of an edge angle of at least one leading edge and / or trailing edge extends in a plane parallel to the longitudinal extension of this at least one leading edge and / or trailing edge extending center plane of the component.
  • a structure of the component of areas of fiber ceramic material is mirror-symmetrical with respect to the median plane.
  • Layers of fibrous ceramic material are also, in particular, layers of fibrous ceramic material, such as the middle layer.
  • the mirror symmetry is observed on macroscopic observation, i. concerning the shape, the arrangement and the material type of the areas, but not their fine structure and their exact material composition.
  • the first region and / or the second region are formed as layers of fiber-ceramic material.
  • the component then has a layer structure; this may include further layers in addition to the middle layer and the layers of the first and the second region.
  • the component has at least one intermediate layer of fiber-ceramic material, to which on a first and a second Side adjacent directly to a layer of fiber-ceramic material, wherein a ceramic content of the fiber-ceramic material of the intermediate layer between a ceramic content of the adjacent on the first side layer and a ceramic content of the adjacent on the second side layer.
  • a gradation gives a strong bond between the layers, which contributes to a high stability of the component.
  • the component has a layer structure of layers of fiber-ceramic material, in which layers of a respective fiber-ceramic material with a relatively high ceramic content and layers of a respective fiber-ceramic material with a relatively low ceramic content are arranged in a stacking direction of the layers. Relatively high ceramic contents of the materials of a first number of layers and relatively low ceramic contents of the materials of a second number of layers are given when the material of each layer of the first number has a higher ceramic content than the material of each layer of the second number. By this measure, the resistance of the component is increased.
  • one or more of the intermediate layers described above can also be provided between a layer of a fibrous ceramic material with a relatively high ceramic content and a layer adjacent to it of a fibrous ceramic material with a relatively low ceramic content.
  • the component has a cover layer of fiber-ceramic material, wherein the fiber-ceramic material of the cover layer has a higher ceramic content than the fiber-ceramic material of the middle layer.
  • a cover layer on which an extended surface of the component is formed, meets in a hot gas flow, a large number of corrosive and abrasive particles, so it is beneficial if their fiber ceramic material has a high ceramic content and thus a high abrasion resistance.
  • the construction of the component from different areas, i. In particular, also layers, and their respective fiber-ceramic material are determined depending on the temperature requirements and the loads caused by the hot gas flow in the respective intended application.
  • the fibrous ceramic material of at least one region is or comprises a carbide ceramic material.
  • the fiber-ceramic material of at least one region contains C fibers (carbon fibers) or SiC fibers (silicon carbide fibers).
  • the fibrous ceramic material of the at least one region is or comprises a C / C-SiC material or a SiC / SiC material.
  • a fiber ceramic material is referred to carbon fibers in a matrix of carbon and silicon carbide.
  • carbon fibers are first embedded in a matrix of a carbon-containing matrix polymer. Pyrolysis of the matrix polymer subsequently produces a carbon matrix. In a subsequent addition of liquid silicon this forms with a portion of the carbon of the carbon matrix silicon carbide, so that under ceramization Carbon and silicon carbide containing matrix is formed. This process is also referred to as the liquid silicon infiltration (LSI) process.
  • LSI liquid silicon infiltration
  • the strength of their binding to the carbonaceous matrix polymer can be influenced in an LSI process.
  • large areas of the pyrolyzed body are accessible to the liquid silicon, so that a high silicon carbide content and thus a high ceramic content is achieved. Therefore, the ceramic content of the C / C-SiC material can be adjusted by thermal pretreatment of the carbon fibers.
  • An SiC / SiC material consists of silicon carbide fibers in a silicon carbide matrix. It can be made by depositing a silicon carbide matrix from a gaseous precursor component of silicon carbide fibers in a so-called "chemical vapor infiltration” (CVI) process.
  • CVI chemical vapor infiltration
  • the middle layer consists of a C / C-SiC-XB material.
  • This material type has a low ceramic content and thus a high mechanical strength.
  • first region and / or the second region advantageously consist of a C / C-SiC-XD material.
  • This type of material has a high ceramic content and high abrasion resistance.
  • C / C-SiC-XT materials and C / C-SiC XC materials. These can be used, for example, for intermediate layers between a respective layer of a C / C-SiC-XB material and a layer of a C / C-SiC-XD material.
  • the fiber-ceramic material of at least one region is made at least partially from a biomorphic material.
  • a precursor material can be prepared, which can then be converted by pyrolysis and ceramization to a SiC material.
  • the fiber-ceramic material of at least one region contains fibers which are arranged in the form of a felt, a fleece, a roll, a mat, a fabric or a braid.
  • a semi-finished fiber in which the fibers are arranged in the respective structure.
  • the component is designed as a thruster.
  • the component may also be another component provided with at least one leading edge and / or trailing edge for use in a hot gas flow, which may be determined, for example, for use in a rocket engine or in a power plant, in particular in its boiler area.
  • the component according to the invention can be produced, for example, by means of an autoclave method, a pressing method or a "Resin Transfer Molding" method (RTM method).
  • a preform with fibers embedded in a matrix polymer can be obtained by the methods mentioned.
  • the preform may have a defined structure of different areas, in particular a layer structure, wherein different materials are used for the different areas can.
  • the preform for producing the fiber-ceramic material of the component as a whole can be subjected to the steps of pyrolysis and ceramization of an LSI process. After the ceramization can be obtained by a post-processing such as grinding or milling the desired shape of the component.
  • a pressing technique one starts from arranged in the desired structure, impregnated with a liquid matrix component semi-finished fiber.
  • the curing of the matrix component to the matrix polymer is made in this case, however, in a mold.
  • a pressing technique for producing a thruster is, for example, in WO 2006/010502 A2 described.
  • the semi-finished fiber products in the desired structure are introduced into an infiltration mold.
  • the infiltration mold is sealed before a liquid matrix component is fed into it.
  • the matrix component then soaks through the semi-finished fiber products and is cured in the infiltration mold.
  • the number and shape of the areas of fiber-ceramic material of the component according to the invention and in particular also the thickness of layers of fiber-ceramic material can thus be determined by an appropriate selection of semi-finished fiber products used in the production of the preform.
  • FIG. 1 shows an exemplary embodiment of an engine for a flying object denoted by 10 there.
  • a propellant 14 is arranged with a solid fuel in a housing 12.
  • the propellant 14 may be provided with a central channel 16.
  • a tail cone 20 connects, in which a nozzle 22 is arranged.
  • this nozzle 22 is penetrated by a hot gas flow 24, which forms during the burning of the propellant charge 14.
  • the hot gas flow 24 exits the housing 12 in the region of the end 18.
  • the hot gas flow 24 enters a propellant-side end 26 of the nozzle 22 and from an outlet end 28 of the nozzle 22 in the environment, wherein the nozzle 22 between the propellant-side end 26 and the outlet end 28 has a constriction 30.
  • Thrusters 32a, 32b are provided near the outlet end 28 of the nozzle 22. They serve to influence the hot gas flow 24 immediately before exiting through the exit end 28 in order to direct the flying object provided with the engine 10.
  • the hot gas flow 24 may carry particles with it.
  • the thrusters 32a, 32b are therefore typically exposed in the hot gas flow 24 to both aerodynamic loads and abrasive loads. For the life of the thrusters 32a, 32b in particular their stability in the areas critical where they each have an acute-angled leading edge or trailing edge.
  • the tail cone 20 includes, for example, additional external, air-stabilizing air guide surfaces 34, which are also referred to as fins.
  • An embodiment of a thruster according to the invention which in FIG. 2 shown in perspective and denoted by 40, comprises a Wing 42 and connected to the wing 42 shaft 44.
  • the wing 42 is exposed to the operation of a flying object of the hot gas flow 24.
  • the thruster 40 is rotatably mounted in the nozzle 22.
  • the shaft 44 thus serves as a fastening bolt for fixing the wing 42 to the nozzle 22.
  • the wing 42 of the thruster 40 has the geometry of an approximated truncated pyramid.
  • An underside 46 of the blade which corresponds to a base of the approximated truncated pyramid, is approximately formed in the form of a hexagon compressed perpendicular to one of its sides.
  • a leading edge 48 and a trailing edge 50 are formed at opposite ends of the wing 42.
  • the angle between the adjoining side surfaces is exemplarily about 30 °, at the trailing edge by way of example about 25 °.
  • Both the leading edge and the trailing edge are rounded, so that they are both planar and have both a finite longitudinal extent and a finite transverse extent.
  • the longitudinal extent 52 of the leading edge 48 is shown.
  • Two flow guide surfaces of the wing 42 which are connected to each other both on the leading edge 48 and the trailing edge 50 and of which a flow guide surface 54 a in FIG. 3 is visible, include each three adjacent side surfaces of the approximated truncated pyramid of the wing 42nd
  • the orientation of the jet rudder 40 is selected so that the leading edge 48 faces in a direction which is substantially opposite to a flow direction of the hot gas flow 24, while the trailing edge 50 faces in a direction substantially parallel to the flow direction of the hot gas flow 24.
  • the shaft 44 of the thruster 40 is formed for example by means of a cylindrical element, wherein a base surface of the cylinder of the shaft 44 is arranged in centered position on the underside 46 of the wing 42.
  • FIG. 3 is a cross-sectional view of a first embodiment of a thruster 60 according to the invention, which the in FIG. 2 has shown shape, along the line AA in FIG. 2 played.
  • Elements shown are in FIG. 3 denoted by the same reference numerals as in FIG. 2 ,
  • a middle layer 62 of fiber-ceramic material is disposed between a first region 64a of fiber-ceramic material and a second region 64b of fiber-ceramic material.
  • the fibrous ceramic material of the middle layer 62 has a lower ceramic content than the fibrous ceramic material of the first and second regions 64a, 64b.
  • the middle layer 62 is made of a C / C-SiC-XB material
  • the first and second regions 64a, 64b are made of a C / C-SiC-XD material.
  • the middle layer 62 is flat and extends across the thruster 60.
  • An in FIG. 2 shown running direction 65 of the middle layer 62 is parallel to the longitudinal extent 52 of the leading edge 48; Both the leading edge 48 and the trailing edge 50 are formed on the middle layer 62.
  • leading edge 48 is a portion of the surface of the thruster 60 through which the two flow guide surfaces 54a, 54b are interconnected. It has in addition to the finite longitudinal extent 52 and a finite transverse extent 66. Its edge angle 68 is the angle that in the plane of the cross-sectional view according to FIG. 4 which is perpendicular to the longitudinal extent 52 of the leading edge 48, between the tangential planes 70a, 70b of the flow guide surfaces 54a, 54b at the points 72a, 72b, where they are adjacent to the leading edge 48, respectively.
  • the edge angle 68 of the leading edge 48 here corresponds to the angle at which these side surfaces extend to one another. It is about 30 °.
  • the correspondingly defined edge angle of the trailing edge 50 is about 25 °.
  • the leading edge 48 is formed both over its entire longitudinal extent 52 and over its entire transverse extent 66 at the middle layer 62. In addition, 48 are also on the leading edge to each other Connected near edge portions 74a, 74b of the flow guide surfaces 54a, 54b formed on the middle layer 62.
  • the edge angle 68 of the leading edge 48 has an angle bisector 76, which lies within the thruster 60 in the middle layer 62.
  • This bisecting line 76 extends in a plane parallel to the longitudinal extent 52 of the leading edge 48 extending center plane of the thruster 60, with respect to which the structure of the thruster 60 is made of fiber ceramic material is mirror-symmetrical, so that there is a simple structure.
  • the bisector 76 of the edge angle 68 of the leading edge 48 is also an angle bisector of the edge angle of the trailing edge 50th
  • leading edge 48 and trailing edge 50 forming surface portions of the thruster 60 and the near edge portions of the flow guide surfaces 54a, 54b at the leading edge 48 (where the near edge portions are denoted by reference numerals 74a, 74b) and at the trailing edge 50 are in this structure a material with a relatively low ceramic content, which has a relatively high mechanical strength.
  • a high stability of the component at the leading edge 48 and the trailing edge 50 is achieved, in particular the risk of breakage at these edges is reduced.
  • edge-remote sections 78a, 78b of the flow guide surfaces 54a, 54b are formed on the first region 64a and the second region 64b, the material of which each has a relatively high ceramic content. Therefore, the component has high abrasion and corrosion resistance in these surface portions occupying most of the flow guide surfaces 54a, 54b.
  • the middle layer 62 serves as the aerodynamically supporting position of the thruster 60. Because of its extension across the entire component from the leading edge 48 to the trailing edge 50, it can increase the stability of the thruster 60 to a large extent.
  • the thruster 60 may be made of fiber ceramic material as a whole, that is, including the shaft 44.
  • the areas of fiber-ceramic material extend in the in FIG. 3 shown arrangement over the entire extent of both the wing 42 and the shaft 44th
  • FIG. 5 is a cross-sectional view of a second embodiment of a thruster 80 according to the invention, which the in FIG. 2 has shown shape, along the line AA in FIG. 2 played.
  • Elements shown are in FIG. 5 denoted by the same reference numerals as in FIG. 2 ,
  • a middle layer 82 is arranged in the same manner as in FIG Figures 3 and 4 shown first embodiment.
  • the leading edge 48 and the trailing edge 50 are each formed over the entire longitudinal extension and its entire transverse extent at the middle layer 82. Also on the leading edge 48 and the trailing edge 50 respectively adjacent edge near portions of both flow guide surfaces 54a, 54b of the thruster 60 are formed on the middle layer 82. This results in the advantages already described in connection with the first embodiment.
  • the middle layer 82 On the two sides of the middle layer 82, however, a plurality of further layers of fiber-ceramic material is provided in this second embodiment.
  • the thruster 80 has a center plane in which a common bisector 86 of the edge angle of the leading edge 48 and the trailing edge 50 extends and parallel to the longitudinal extent 52 of the leading edge 48 and the longitudinal extent of the trailing edge 50 extends.
  • the structure of the thruster 80 of areas of ceramic fiber material is mirror-symmetrical with respect to this center plane.
  • the layer structure of the thruster 80 on the middle layer 82 side, on which the layer of the first region 84a is disposed will be described in more detail. Due to the mirror symmetry of the thruster 80 applies on the side of the middle layer 82, on which the position of the second region 84 b is arranged.
  • the middle layer 82 and the layer of the first region 84a each directly adjoin an intermediate layer 88 of fibrous ceramic material disposed therebetween, wherein a ceramic content of the fibrous ceramic material of the intermediate layer 88 is between the ceramic content of the fibrous ceramic material of the middle layer 82 and the ceramic content of the ceramic fiber Material of the location of the first area 84a is located. From the middle layer 82 to the position of the first region 84a, the ceramic content is graded therewith, whereby a strong cohesion between the layers is achieved.
  • FIG. 5 By way of example, five outer layers 92a, 92b, 92c, 92d, 92e are shown.
  • the alternating arrangement of relatively high material and relatively low ceramic content material in the stacking direction 90 provides increased stability of the thruster 80 over the stresses encountered in the hot gas flow 24.
  • a large number of outer layers 92 are present. This is possible with a given extension of the thruster 80 in the stacking direction 90 by the choice of a small thickness of the individual layers of fiber-ceramic material.
  • the furthest spaced from the middle layer 82 outer layer 92e forms a cover layer of the component.
  • the middle layer 82 is comprised of a C / C-SiC-XB material, the layer of the first region 84a, and the relatively high ceramic content outer layers 92b, 92d of a C / C-SiC-XD material.
  • the thruster 60 as a whole including the stem 44 may be made of fiber-ceramic material. Then, the layers of fibrous ceramic material extend in the in FIG. 5 shown arrangement over the entire extent of both the wing 42 and the shaft 44th
  • the component of the invention which may be in particular a thruster, optimized in terms of its resistance to the occurring in a hot gas flow aerodynamic and abrasive loads. Because at least one acute-angled Leading edge and / or trailing edge is provided at the middle layer, in particular the risk of breakage is reduced at this at least one leading edge and / or trailing edge. This leads to a longer life of the component.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Woven Fabrics (AREA)
  • Laminated Bodies (AREA)
  • Ceramic Products (AREA)
  • Gas Burners (AREA)

Claims (15)

  1. Composant utilisable dans des écoulements de gaz chaud qui comprend une première zone (64a ; 84a) de matériau de fibres céramiques, une deuxième zone (64a, 84b) de matériau de fibres céramiques et une couche médiane (62 ; 82) de matériau de fibres céramiques, disposée entre la première zone (64a ; 84a) et la deuxième zone (64b ; 84b), dans lequel au moins un bord d'attaque à angle aigu (48) et/ou un bord de fuite (50) du composant est formé sur la couche médiane (62 ; 82), caractérisé en ce que le matériau de fibres céramiques de la couche médiane (62 ; 82) présente une teneur en céramique inférieure à celle du matériau de fibres céramiques de la première zone (64a ; 84a) et de la deuxième zone (64b ; 84b).
  2. Composant selon la revendication 1, caractérisé en ce que l'au moins un bord d'attaque (48) et/ou bord de fuite (50) est formé au moins sur une partie d'une étendue longitudinale terminale (52) sur la couche médiane (62 ; 82) et en particulier, en ce que l'au moins un bord d'attaque (48) et/ou bord de fuite (50) est formé sur toute son étendue longitudinale (52) sur la couche médiane (62 ; 82).
  3. Composant selon l'une des revendications précédentes, caractérisé en ce que l'au moins un bord d'attaque (48) et/ou bord de fuite (50) présente une étendue transversale (66) terminale qui est transversale à son étendue longitudinale (52) et en particulier en ce que l'au moins un bord d'attaque (48) et/ou bord de fuite (50) est formé au moins sur une partie de son étendue transversale (66) sur la couche médiane (62 ; 82), et en particulier en ce que l'au moins un bord d'attaque (48) et/ou bord de fuite sur toute son étendue transversale (66) est formé sur la couche médiane (62 ; 82) et en particulier en ce que, à la fois l'au moins un bord d'attaque (48) et/ou bord de fuite (50) sont formés sur toute leur étendue transversale (66) et également au moins un segment (74a ; 74b) proche du bord, jouxtant l'au moins un bord d'attaque (48) et/ou bord de fuite (50) d'une surface de conduction de l'écoulement (54a ; 54b) du composant est formé sur la couche médiane (62 ; 82).
  4. Composant selon l'une des revendications précédentes, caractérisé en ce qu'une direction d'évolution (65) de la couche médiane (62 ; 82) vers l'étendue longitudinale (52) de l'au moins un bord d'attaque (48) et/ou bord de fuite (50) est parallèle.
  5. Composant selon l'une des revendications précédentes, caractérisé en ce qu'une bissectrice (76 ; 86) d'un angle de bord (68) d'au moins un bord d'attaque (48) et/ou un bord de fuite (50) se situe à l'intérieur du composant dans la couche médiane (62 ; 82).
  6. Composant selon l'une des revendications précédentes, caractérisé en ce qu'une bissectrice (76 ; 86) d'un angle de bord (68) d'au moins un bord d'attaque (48) et/ou bord de fuite (50) évolue dans un plan médian du composant, parallèlement à l'étendue longitudinale (52) de ce au moins un bord d'attaque (48) et/ou bord de fuite (50), et en particulier en ce qu'une construction du composant des zones de matériau de fibre céramique est symétrique en miroir par rapport au plan médian.
  7. Composant selon l'une des revendications précédentes, caractérisé en ce que la première zone (64a ; 84a) et/ou la deuxième zone (64b ; 84b) sont formées comme des couches de matériau de fibres céramiques.
  8. Composant selon l'une des revendications précédentes, caractérisé en ce que le composant présente au moins une couche intermédiaire (88) de matériau à fibres céramiques, que jouxte directement sur un premier et un deuxième côté respectivement, une couche (82 ; 84a) de matériau de fibres céramiques, dans lequel une teneur en céramique du matériau à fibres céramiques de la couche intermédiaire se situe entre une teneur en céramique de la couche (82) jouxtant le premier côté et une teneur en céramique de la couche (84a) jouxtant le deuxième côté.
  9. Composant selon l'une des revendications précédentes, caractérisé en ce que le composant présente une structure de couche constituée de couches de matériau à fibres céramiques, dans laquelle sont disposées dans un sens d'empilement (90) des couches, des couches alternantes (84a ; 92b ; 92d) respectivement d'un matériau de fibres céramique présentant une teneur en céramique relativement élevée et des couches (82 ; 92a : 92c ; 92e) respectivement d'un matériau de fibres céramiques présentant une teneur en céramique relativement faible.
  10. Composant selon l'une des revendications précédentes, caractérisé en ce que le composant présente une couche de couverture (92e) de matériau de fibres céramiques, dans lequel le matériau de fibres céramiques de la couche de couverture (92e) présente une teneur en céramique supérieure à celle du matériau de fibres céramiques de la couche médiane (82).
  11. Composant selon l'une des revendications précédentes, caractérisé en ce que le matériau de fibres céramiques est ou comprend au moins une zone de matériau de céramique au carbure.
  12. Composant selon l'une des revendications précédentes, caractérisé en ce que le matériau de fibres céramiques contient au moins une zone de fibres de C ou de fibres de SiC et en particulier en ce que le matériau de fibres céramiques de l'au moins une zone est ou présente un matériau de C/C-SiC ou un matériau de SiC/SiC et en particulier en ce que la couche médiane est constituée d'un matériau de C/C-SiC-XB et en particulier en ce que la première zone et/ou la deuxième zone sont constituées d'un matériau de C/C-SiC-XD.
  13. Composant selon l'une des revendications précédentes, caractérisé en ce que le matériau de fibres céramiques d'au moins une zone est au moins en partie fabriqué en une matière biomorphe.
  14. Composant selon l'une des revendications précédentes, caractérisé en ce que le matériau de fibres céramiques d'au moins une zone contient des fibres qui sont disposées sous la forme d'un feutre, d'une nappe, d'un ruban, d'une natte, d'un tissu ou d'un treillis.
  15. Composant selon l'une des revendications précédentes, caractérisé par une formation en système de déviation de courant (60 ; 80).
EP10154480.7A 2009-03-06 2010-02-24 Composant utilisable dans des écoulements de gaz chaud Active EP2230394B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009013150A DE102009013150B4 (de) 2009-03-06 2009-03-06 Bauteil zum Einsatz in Heißgasströmungen

Publications (3)

Publication Number Publication Date
EP2230394A2 EP2230394A2 (fr) 2010-09-22
EP2230394A3 EP2230394A3 (fr) 2014-04-16
EP2230394B1 true EP2230394B1 (fr) 2015-07-15

Family

ID=42373725

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10154480.7A Active EP2230394B1 (fr) 2009-03-06 2010-02-24 Composant utilisable dans des écoulements de gaz chaud

Country Status (3)

Country Link
US (1) US8268438B2 (fr)
EP (1) EP2230394B1 (fr)
DE (1) DE102009013150B4 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FI20105048A (fi) * 2010-01-21 2011-07-22 Runtech Systems Oy Menetelmä radiaalikompressorin juoksupyörän valmistamiseksi
CN107401956B (zh) * 2017-08-09 2020-07-07 南京航空航天大学 基于喉道偏移式气动矢量喷管的两栖巡航导弹及其姿态控制方法
US11352978B2 (en) 2020-06-24 2022-06-07 Raytheon Company Deflectable distributed aerospike rocket nozzle

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3738107C1 (en) 1987-11-10 1989-06-22 Messerschmitt Boelkow Blohm Device for deflecting a fluid jet with the aid of a jet control surface
US5806791A (en) 1995-05-26 1998-09-15 Raytheon Company Missile jet vane control system and method
DE19632893C2 (de) * 1996-08-16 2001-02-08 Industrieanlagen Betr Sgmbh Ia Verfahren zur Herstellung von Flugkörperkomponenten aus faserverstärkter Keramik
DE19856597B4 (de) 1998-10-14 2004-07-08 Industrieanlagen-Betriebsgesellschaft Mbh Schutzpanzerung
US6548794B2 (en) * 2001-03-13 2003-04-15 Raytheon Company Dissolvable thrust vector control vane
DE10143015C2 (de) 2001-09-03 2003-11-13 Deutsch Zentr Luft & Raumfahrt Verfahren zur Herstellung eines Verbundwerkstoffes
NO318772B1 (no) * 2003-09-24 2005-05-02 Nammo Raufoss As Rakettmotor med styrevinger i motorens dyse
DE102004037487A1 (de) 2004-07-27 2006-03-23 Deutsches Zentrum für Luft- und Raumfahrt e.V. Strahlruder und Verfahren zur Herstellung eines Strahlruders
US7549840B2 (en) * 2005-06-17 2009-06-23 General Electric Company Through thickness reinforcement of SiC/SiC CMC's through in-situ matrix plugs manufactured using fugitive fibers
US7568348B2 (en) * 2005-11-28 2009-08-04 Aerojet-General Corporation Nozzle assembly for rocket and ramjet applications

Also Published As

Publication number Publication date
US20100223906A1 (en) 2010-09-09
US8268438B2 (en) 2012-09-18
DE102009013150A1 (de) 2010-09-16
DE102009013150B4 (de) 2011-05-05
EP2230394A2 (fr) 2010-09-22
EP2230394A3 (fr) 2014-04-16

Similar Documents

Publication Publication Date Title
EP2733063B1 (fr) Structure de morphing pour un bord d'attaque d'une aile d'avion
DE3539091A1 (de) Stromlinien-rotorschaufel
DE102009006418A1 (de) Turbinenschaufel, insbesondere Laufschaufel für eine Dampfturbine, sowie Herstellungsverfahren hierfür
EP3199451A1 (fr) Nez de rotor d'un ventilateur de moteur à propulsion
EP2230394B1 (fr) Composant utilisable dans des écoulements de gaz chaud
DE102008059653B4 (de) Flächiges Bauteil eines Fluggerätes und Verfahren zu dessen Herstellung
EP2699764B1 (fr) Aube pour une turbomachine thermique
WO2017129686A2 (fr) Bride de longeron et son procédé de fabrication
DE102016101663A1 (de) Holmgurt und Herstellungsverfahren
EP1771700B1 (fr) Deviateur de jet et procede pour produire ce dernier
DE102012102746A1 (de) Rotorblatt mit adaptivem Vorflügel für eine Windenergieanlage
EP1988012B1 (fr) Aile d'un aéronef avec une structure porteuse en matériau composite renforcé de fibres
WO2005015063A1 (fr) Anneau de glissement et systeme d'etancheite a anneau de glissement pour moteurs a reaction
DE102020107743A1 (de) Hybridfaser und Verfahren zu ihrer Herstellung
DE102010023496B4 (de) Rumpfsegment eines Flugzeugs
DE102019110693A1 (de) Druckentlastungsvorrichtung mit einer Druckentlastungsklappe
EP3615321B1 (fr) Procédé pour la fabrication simultanée de deux éléments composites fibreux ou plus
DE102013225572A1 (de) Seilsicherung für Strömungsmaschinen
DE102011050801A1 (de) Verfahren zum Enteisen von Rotorblättern eines Hubschraubers und Vorrichtung zur Durchführung des Verfahrens an dem Hubschrauber
WO2011082866A1 (fr) Corps armé par des fibres
DE202023002701U1 (de) Batteriegehäusedeckel mit einem Abschnitt umfassend einen Faserverbund mit oxidischer Matrix
DE102023103668A1 (de) Batteriegehäusedeckel mit einem Abschnitt umfassend einen Faserverbund mit oxidischer Matrix
DE202022000922U1 (de) Flügel, Rotorblätter, Turbinen, Finnen und Schiffsschrauben aus CFS
DE10330166A1 (de) Gepanzertes Fahrzeug
DE10224857B4 (de) Gleitelement für Hochgeschwindigkeitsanwendungen und Verfahren zu dessen Herstellung

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F02K 9/90 20060101AFI20140307BHEP

Ipc: F42B 10/66 20060101ALI20140307BHEP

17P Request for examination filed

Effective date: 20141015

RBV Designated contracting states (corrected)

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150211

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502010009852

Country of ref document: DE

Representative=s name: HOEGER, STELLRECHT & PARTNER PATENTANWAELTE MB, DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 736940

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150815

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010009852

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20150715

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151015

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151016

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151116

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010009852

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

26N No opposition filed

Effective date: 20160418

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160224

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160224

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20161028

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160224

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160224

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 736940

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160224

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160224

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20100224

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502010009852

Country of ref document: DE

Representative=s name: HOEGER, STELLRECHT & PARTNER PATENTANWAELTE MB, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240109

Year of fee payment: 15